全三维轴流式透平叶栅离散伴随气动优化设计
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摘要
在前期研究的基础上,将三维轴流式透平叶栅参数化方法发展为基于非均匀有理B样条(NURBS)技术的新型叶栅参数化方法。此方法在对叶栅型线进行NURBS曲线拟合的同时,将叶栅各截面重心及安装角也纳入参数化范围,大大扩展了优化设计空间。基于此,应用离散伴随气动优化设计系统,对Aachen第一级静叶栅在无粘、大负攻角流动条件下,以降低叶栅进出口总压损失为目标进行了全三维气动优化设计。优化后叶栅总压系数提高了1.64%,通道内的流动分离状况得到了有效改善。此外,对优化过程是否添加质量流量约束进行的研究表明,约束条件对优化效果有较大影响,实际应用中应根据需要进行具体的优化设置。
Based on the previous work, the previous parameterization method was developed to a new parameterization method based on Non-uniform Rational B-Spline(NURBS) technology. By this method, the stack points, the stagger angles, as well as the blade profiles can be parameterized at the same time to enlarge the optimization design space. By combining the new parameterization method and the aerodynamic optimization design platform based on discrete adjoint method, the first row stator of Aachen turbine was fully 3 D optimized with objective to minimize the total pressure loss through the cascade passage under inviscid and a big negative incidence flow condition. After optimization, the total pressure coefficient has increased 1.64%, and the flow separation on pressure side of the blade was improved. Besides, the optimization designs with and without the mass flow constraint were studied. And the results show that the constraint has a great influence on the optimization effect and the optimization details need to be set up where necessary in practical application.
Based on the previous work, the previous parameterization method was developed to a new parameterization method based on Non-uniform Rational B-Spline(NURBS) technology. By this method, the stack points, the stagger angles, as well as the blade profiles can be parameterized at the same time to enlarge the optimization design space. By combining the new parameterization method and the aerodynamic optimization design platform based on discrete adjoint method, the first row stator of Aachen turbine was fully 3 D optimized with objective to minimize the total pressure loss through the cascade passage under inviscid and a big negative incidence flow condition. After optimization, the total pressure coefficient has increased 1.64%, and the flow separation on pressure side of the blade was improved. Besides, the optimization designs with and without the mass flow constraint were studied. And the results show that the constraint has a great influence on the optimization effect and the optimization details need to be set up where necessary in practical application.
引文
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[2]Papadimitriou D I,Giannakoglou K C.Direct,Adjoint and mixed approaches for the computation of hessian in airfoil design problems[J].International Journal for Numerical Methods in Fluids,2008,56(10):1929-1943.
[3]Duta M C,Giles M B,Campobasso M S.The harmonic ad.joint approach to unsteady turbomachinery design[J].Inter.national Journal for Numerical Methods in Fluids,2002,3(3-4):323-332.
[4]Campobasso M S,Duta M C,Giles M B.Adjoint calcula.tion of sensitivities of turbomachinery objective functions[J].AIAA Journal of Propulsion and Power,2003,19(4):693-703.
[5]Zhang C L,Feng Z P.Aerodynamic shape design optimiza.tion for turbomachinery cascade based on discrete adjoint method[R].ASME GT2011-45805,2011.
[6]Lu J,Zhang C L,Feng Z P.Aerodynamic Optimization and inverse designs of 2D and 3D turbine cascades using dis.crete adjoint method[R].ASME GT2013-95284,2013.
[7]张朝磊,厉海涛,丰镇平.基于离散伴随方法的透平叶栅气动优化设计[J].工程热物理学报,2012,33(1):47-50.
[8]张朝磊,卢娟,丰镇平.基于离散伴随方法的透平叶栅反设计[J].工程热物理学报,2012,33(4):583-586.
[9]卢娟,张朝磊,丰镇平.离散伴随气动优化设计方法的紊流扩展[J].西安交通大学学报,2013,47(1):37-42.
[10]李剑白,卿雄杰,周山,等.涡轮叶片气动设计软件BladeDesign[J].燃气涡轮试验与研究,2011,24(3):11-16.
[11]皮尔L,特莱尔W.非均匀有理B样条[M].第二版.赵罡,穆国旺,王拉柱,译.北京:清华大学出版社,2010.
[12]Tutorials,FINETM/Turbo v8.c,Documentation v8-c[Z/OL].http://www.numeca.com.
[2]Papadimitriou D I,Giannakoglou K C.Direct,Adjoint and mixed approaches for the computation of hessian in airfoil design problems[J].International Journal for Numerical Methods in Fluids,2008,56(10):1929-1943.
[3]Duta M C,Giles M B,Campobasso M S.The harmonic ad.joint approach to unsteady turbomachinery design[J].Inter.national Journal for Numerical Methods in Fluids,2002,3(3-4):323-332.
[4]Campobasso M S,Duta M C,Giles M B.Adjoint calcula.tion of sensitivities of turbomachinery objective functions[J].AIAA Journal of Propulsion and Power,2003,19(4):693-703.
[5]Zhang C L,Feng Z P.Aerodynamic shape design optimiza.tion for turbomachinery cascade based on discrete adjoint method[R].ASME GT2011-45805,2011.
[6]Lu J,Zhang C L,Feng Z P.Aerodynamic Optimization and inverse designs of 2D and 3D turbine cascades using dis.crete adjoint method[R].ASME GT2013-95284,2013.
[7]张朝磊,厉海涛,丰镇平.基于离散伴随方法的透平叶栅气动优化设计[J].工程热物理学报,2012,33(1):47-50.
[8]张朝磊,卢娟,丰镇平.基于离散伴随方法的透平叶栅反设计[J].工程热物理学报,2012,33(4):583-586.
[9]卢娟,张朝磊,丰镇平.离散伴随气动优化设计方法的紊流扩展[J].西安交通大学学报,2013,47(1):37-42.
[10]李剑白,卿雄杰,周山,等.涡轮叶片气动设计软件BladeDesign[J].燃气涡轮试验与研究,2011,24(3):11-16.
[11]皮尔L,特莱尔W.非均匀有理B样条[M].第二版.赵罡,穆国旺,王拉柱,译.北京:清华大学出版社,2010.
[12]Tutorials,FINETM/Turbo v8.c,Documentation v8-c[Z/OL].http://www.numeca.com.